Systems and methods with distributed bleed for gas turbine engine compressor stabilization

Patent metadata

Field	Value
Publication number	US-12196141-B2
Application number	US-202318303111-A
Country	US
Kind code	B2
Filing date	Apr 19, 2023
Priority date	Apr 19, 2023
Publication date	Jan 14, 2025
Grant date	Jan 14, 2025

Abstract

Systems and methods for stable operation of a compressor of a gas turbine engine include axial stages, each including a series of rotor blades. A centrifugal stage has a centrifugal impeller disposed downstream from the axial stages. Air flows through the compressor first through the axial stages and then through the centrifugal stage. Each respective axial stage includes mechanisms for the avoidance of certain operating conditions of the compressor such as surge. The mechanisms include variable vane sets disposed upstream from a series of the rotor blades or a bleed port or ports around the respective axial stage downstream from the series of rotor blades to selectively extract air from the respective axial stage.

First claim

What is claimed is:

1. A system for stable operation of a compressor of a gas turbine engine, the system comprising:
axial stages, each respective axial stage in the axial stages including a rotor, each rotor having rotor blades;
a centrifugal stage having a centrifugal impeller disposed downstream from the axial stages,
wherein air flows through the compressor first through the axial stages and then through the centrifugal stage,
wherein each and every respective axial stage of the axial stages is configured for avoidance of certain operating conditions of the compressor by one of:
a variable vane set disposed upstream from the rotor blades of the respective axial stage, the variable vane set configured to vary relative to rotational speed of the compressor; or
at least one bleed port around the respective axial stage, the at least one bleed port configured to selectively extract air from the respective axial stage,
wherein a plural number of the axial stages include the at least one bleed port so that bleed from the gas turbine engine is distributed among the plural number of axial stages,
wherein each individual stage of the plural number of the axial stages is configured with the at least one bleed port being disposed at a location that is downstream from the rotor blades of the respective individual axial stage and,
wherein at least one of the axial stages include the variable vane set,
wherein the variable vane sets include inlet guide vanes and stator vanes and further comprising:
a bleed control valve configured to control flow through the at least one bleed port;
a bleed control actuator at each respective bleed control valve configured to move the respective bleed control valve to open and close;
an inlet guide vane actuator coupled with the inlet guide vanes to move the inlet guide vanes in opening and closing directions;
at least one stator actuator coupled with the stator vanes of at least one of the axial stages to move the stator vanes in opening and closing directions; and
at least one controller coupled with the bleed control actuators, the inlet guide vane actuator, and the at least one stator actuator, the controller configured to:
determine whether the compressor is approaching the certain operating conditions; and
operate, based on the speed and when the compressor is approaching the certain operating conditions, the inlet guide vanes through the inlet guide vane actuator, the stator vanes through the stator actuator, and the at least one bleed port through the bleed control actuators, for any combination of the axial stages to avoid the certain operating conditions.

2. The system of claim 1 , wherein each individual stage of the plural number of axial stages includes the stator vanes disposed downstream from the rotor of the respective individual stage, wherein the at least one bleed port of the respective individual stage is disposed at a location that is downstream from the stator vanes of the same respective individual stage.

3. The system of claim 1 , wherein the variable vane set and the at least one bleed port are not included in the centrifugal stage to maintain stability of the compressor.

4. The system of claim 1 , comprising a controller configured to:
monitor a speed of the engine;
determine whether the compressor is approaching the certain operating conditions; and
schedule, based on the speed and when the compressor is approaching the certain operating conditions, operation of the variable vane set and the at least one bleed port for at least one of the axial stages to avoid the certain operating conditions.

5. The system of claim 1 , comprising a controller configured to:
monitor a speed of the engine;
determine whether the compressor is approaching the certain operating conditions;
schedule, based on the speed and when the compressor is approaching the certain operating conditions, operation of the variable vane set and the at least one bleed port for all of the axial stages to avoid the certain operating conditions.

6. The system of claim 1 , wherein the at least one bleed port comprises bleed ports configured so that a total bleed from the gas turbine engine is distributed among every one of the axial stages that do not include the variable vane set by having at least some of the bleed ports at the every one of the axial stages that do not include the variable vane set.

7. The system of claim 1 , comprising a controller configured to:
monitor a speed of the engine;
determine whether the compressor is approaching the certain operating conditions;
schedule, when the compressor is approaching the certain operating conditions and the speed is above a threshold, the variable vane set to move in an opening direction and the at least one bleed port to remain closed; and
schedule, when the compressor is approaching the certain operating conditions and the speed is below the threshold, the variable vane set to moving in a closing direction and the at least one bleed port to open.

8. The system of claim 1 , wherein the certain operating conditions include surge of the compressor, and the variable vane set is controlled to close the variable vane set to reduce flow through, and work input of, the respective stage.

9. The system of claim 1 , comprising:
a bleed control valve configured to control flow through the at least one bleed port;
a bleed control actuator configured to move the bleed control valve to open and close;
a vane actuator coupled with the variable vane set to move the variable vane set in opening and closing directions; and
a controller coupled with the bleed control actuator and the vane actuator, the controller configured to:
determine whether the compressor is approaching the certain operating conditions;
operate, based on the speed and when the compressor is approaching the certain operating conditions, the variable vane sets through the vane actuator, and the at least one bleed port through the bleed control actuator, for any combination of the axial stages to avoid the certain operating conditions.

10. A method for stable operation of a compressor of a gas turbine engine, the method comprising:
including axial stages in the compressor, each respective axial stage in the axial stages having a rotor with rotor blades;
including, downstream from the axial stages, a centrifugal stage in the compressor, the centrifugal stage having a centrifugal impeller disposed;
generating air flows through the compressor first through the axial stages and then through the centrifugal stage;
including, for avoidance of certain operating conditions of the compressor, in each respective axial stage of the axial stages one of a variable vane set disposed upstream from the rotor blades of the respective axial stage, or at least one bleed port around the respective axial stage downstream from the rotor blades of the respective axial stage;
monitoring, by a controller, a speed of the engine;
determining, by the controller, whether the compressor is approaching the certain operating conditions;
scheduling, by the controller when the compressor is approaching the certain operating conditions and the speed is above a threshold, the variable vane set to move in an opening direction and the at least one bleed port to remain closed; and
scheduling, by the controller when the compressor is approaching the certain operating conditions and the speed is below the threshold, the variable vane set to moving in a closing direction and the at least one bleed port to open;
varying, by the variable vane set, an open flow for the air; and
selectively extracting, by the at least one bleed port, air from the respective axial stage.

11

Assignees

• Honeywell Int Inc

Inventors

• Reynolds Bruce David
• Nolcheff Nick
• Bernaud Ryan
• Boyll Greyson

Classifications

• F05D2270/304

  Spool rotational speed · CPC title

• F05D2270/101

  Compressor surge or stall · CPC title

• F04D27/0246

  by varying geometry within the pumps, e.g. by adjusting vanes · CPC title

• F04D27/0223

  Control schemes therefor · CPC title

• F02C9/22

  by adjusting turbine vanes · CPC title